Structural model identification of a small flexible aircraft

Abstract

The system identification of a light-weight, high-aspect ratio wing is presented. Experimental data is obtained from a ground vibration test. The input signals are sine sweep wave forces and the outputs are the corresponding acceleration responses of the aircraft. Subspace algorithms are used to estimate a state-space model of the aircraft. Minimization of the model prediction error is performed to fit the frequency response data. As result, the estimated model identifies six structural modes between 5 Hz and 30 Hz.